The Commercialization of
Space Transportation
April 2007
K-1 Reusable Space Transportation Vehicle
1
NASA Near Term ISS Dilemma

International Space Station (“ISS”)
– Approximately $100 billion investment to date by NASA alone
– U.S. Government obligation to 16-partner countries to operate and provide
cargo and crew transportation to and from ISS through 2015
– NASA currently uses the Space Shuttle to meet this obligation at a cost of
approximately $1 billion per flight
– Space Shuttle to be retired in 2010 – irrevocable decision
– No other NASA capability to meet its commitment through 2015

Only near-term alternatives are Russian launch vehicles and foreign ATVs
(European vehicle) and HTVs (Japanese vehicle)
– U.S. law prohibits use of Russian vehicles after 2011
– ATV and HTV extremely expensive
– None of these alternatives have the ability to return cargo to earth
2
The Opportunity
Decision to
Retire Space
Shuttle in 2010
1978
Space
Shuttle
Flight
1st
Extend life of
the ISS
ISS
OPPORTUNITY
2022
2004
2010
Space Shuttle
Retires
2015
Alternative NASA
Solution
RpK Key Advantages
Lower recurring costs and greater
reliability than any other current ELV
competitor
COTS Program
Rapid launch and re-launch
capability due to reusable design
Positioned to be first-to-market with
ISS re-supply capability
Additional Revenue
Opportunities
Civil and
Military
Payload
Launch
Commercial
Satellite
Delivery
Science and
Technology
Research
Return downmass transportation
capabilities unlike competitors
NASA support
Led by an experienced management
team and supported by its original
world-class team of strategic
partners
3
NASA COTS Program Overview
NASA COTS Program

Two grant recipients, RpK and SpaceX, out of 20 competitors

RpK strengths identified by NASA include:
– Strong management team
– Design and technical maturity of the K-1
– Multiple market approach of the Company’s business plan

Space Act Agreement signed August 18, 2006 provides $207 million to RpK through 2009
– RpK retains nearly all intellectual property and commercial rights to technology (commercial
program in which NASA does not end up owning the launch vehicle)
– NASA provides important resources and technical expertise to the K-1 Program
– NASA will be the Company’s largest customer
– COTS Program is critically important to NASA and its goals

RpK has successfully completed all NASA milestones to date and has received $32.1 million in
milestone payments


Latest Milestone: System Requirements Review
 Met ahead of schedule and under budget
Successful completion of the NASA COTS Program will position RpK to win a commercial
contract for ISS re-supply – a $1 billion annual opportunity
4
K-1 Reusable Space Transportation Vehicle

Designed by Dr. George Mueller, designer of the Apollo and the
Space Shuttle, to leverage existing technologies

Upmass capability: launch cargo and satellite payloads into
space

Downmass capability: return cargo from both inside and
outside Space Station to earth

Fully reusable: designed for 100 flight life – 9-day turnaround

Low-cost provider: starting at $30 million per launch, the K-1
costs significantly less expensive than any existing launch
vehicle
To date, more than $650 million has been invested in design and development of the K-1 vehicle, which is 75% complete
5
RpK Market Opportunities
Unique Fully Reusable Design Will Enable RpK to Successfully Penetrate Multiple Markets
Approx. $1 - 2 Billion Annual
Market Opportunity
Rocketplane Kistler
ISS Re-Supply
(NASA COTS)
Civil and Military
Payload Launch
Commercial Satellite
Delivery
Science &
Technology
Research
First affordable, reusable rocket addressing these markets
6
K-1 Reusable Space Transportation Vehicle
Cargo / Payload Module
 Length: 5.9 m
2nd Stage – Orbital Vehicle (“OV”)
 Length: 18.6 m
 Diameter: 4.3 m
 Weight: 131,800 kg
Key Design Characteristics




1st Stage – Launch Assist Platform
(“LAP”)
 Length: 18.3 m
 Diameter: 6.7 m
 Weight: 250,500 kg

Proven technologies adapted from other successful
aerospace programs and applications reduce both
development cost and technology risk
Use existing flight qualified components (e.g., main
engines)
Designed with high factors of safety, including:
– Triple-string, fault tolerant avionics system ensure
reliable performance flight after flight
– Integrated Vehicle Health Management (“IVHM”)
systems automate and expedite checkout of the
vehicle before and after each flight
Designed for reliability, each K-1 has an expected
life of 100 flights – nine day turnaround
High launch rate and rapid turnaround significantly
reduce the price of access to space
Key Performance Metrics



Approx. 5,700 kg delivered to LEO
Approx. 1,570 kg delivered to GTO
Approx. 2,775 kg of cargo upmass and downmass
for ISS missions
The K-1 design is based on mature, proven technologies
7
K-1: Systems Engineering
RpK’s K-1 Essential Systems Engineering Tasks Are Complete
Overview

Systems engineering for reusable launch vehicles is
dramatically greater than that of ELVs

Both design and verification for the K-1 completed
– Aerodynamics
– Load, dynamics, vibroacoustics
– Thermal
– Mass properties
– Timeline

Trajectory design reference missions completed

Vehicle schematics wiring and plumbing completed

Interface requirements specification completed

Cargo module currently undergoing Preliminary
Design Review
K-1 systems engineering is substantially complete
8
K-1: Development Responsibilities and Status
Vehicle Exterior Structure
• 21 of 23 Major Panels Complete
LAP LOX Tank
• 100% Complete
Parachutes
• Engineering 90% Complete
• Mains – Complete
• Drogue – Complete
• Stabilization – 95% Complete
• Mortar – Complete
• Drop Tests - Complete
OV LOX Tank
• 100% Complete
Thermal Protection System
• Overall Design Complete
• Detailed Design – 30%
• Arc Jet Testing Planned
• Production at Restart
OV RP Tank
• 100% Design Complete
• 35% Fabrication
Payload Module
• 100% Structural Design
Complete
• 25% Fabrication Complete
LAP RP Tank
• 100% RP Design Completed
• 30% Fabrication Complete
OMS Engine
• 40 Igniter Tests Complete
• 29 Injector Tests Complete
LOX Retention Tank
• 100% Design Complete
• 75% Fabrication Complete
AJ-26 Engines
• 9 Engines at Aerojet
AJ-26 Engines
• 37 Engines at Aerojet
• Verification Engine in Test
Airbags
• OV Fabrication 50% Complete
• LAP Fabrication 50% Complete
• ¼ Scale Drop Tests Complete
• Airbag Inflation Tests Complete
Avionics Hardware
• Vehicle Computer – Delivered
• GPS /INS units – Delivered
• TDRSS Receiver – Off the Shelf
• FAA Transponder Delivered
• SMU – In Manufacturing
• PDU, MEC – In Test
Avionics Software
• GN&C Complete
• Hardware in the Loop (HWIL) With Flight
Hardware / Software Testing
Final Assembly
• Commenced 5/98
• 1st Stage LOX Tank
Delivered 6/98
Launch Site
• First Site in Australia
• Contract Executed for Site Design and
Construction
• Launch Site Design 100% complete
• Environmental Approval Received
• Launch Operation Contract Signed
• Native Title Agreement Signed
• Site Ground Breaking
• Export License Approved
• Second Site Planned in U.S.
The K-1 vehicle hardware is 75% complete
9
K-1: Launch Operations
Inclination
(Azimuth)
99º
(-14º)
Spaceport
Woomera
Latitude:
Longitude:
Elevation:
31º South
137º East
541 ft
84º
(5º)
60º
(33º)
Launch Sites Overview
45º
(55º)

RpK plans to have two operational launch sites

First site in Spaceport Woomera, Australia
– Located in Woomera Test Range (“WTR”) in the
South Australian outback
– Launch azimuth covers all addressable market /
customer requirements from one site
– Contract executed for site design and
construction
– Launch site design nearly 100% complete
– Environmental approval received
– Operations agreement signed
– Native title agreement signed
– Technical assistance agreement signed
K-1 launch site provides launch direction that meets customer requirements from one site
10
K-1: ISS Mission Profile Overview
OV Return
Phasing Burn
ISS Altitude
Mated with ISS/Separation
OV De-Orbit Burn
Phasing Altitude to Ldg.
Phasing Altitude to ISS
Coast Phase
LAP Flyback
OV MECO Altitude
OV MECO
OV Re-Entry
Stage Separation
LAP & OV Deploy
Parachutes and
Parachute Deployment Altitude
Land at Launch
Site using Airbags
K-1 Vehicle Liftoff
SPACEPORT WOOMERA: Woomera, S. Aust. 31o S Lat
Typical Event Sequence
Days 1-5 @ ISS
Day 1
Event
LAP Ignition
Stage Separation
OV Ignition
OV MECO
OV Mated with ISS
Time
0:00:00
0:02:20
0:02:27
0:06:19
13:40:00
Event
Crew Unloads Cargo
Crew Loads
Completed
Experiments
Time
Days 1-3
Days 4-5
Assumes 5 day stay at ISS
Day 6
Event
OV Separation from ISS
OV Phases to Landing
OV De-Orbit Burn
OV Re-entry
OV Landing
Time
0:00:00
0:45:00
1:30:00
2:15:00
2:30:00
Time in Hrs:Min:Sec
11
Looking To The Future
12
K-1 Path to the Moon
13